JPH06273100A - Airframe - Google Patents

Abstract

PURPOSE:To provide an airframe which can cover a wide area even if an unexploded bomb occurring rate is reduced, and can perform a duty for a large target. CONSTITUTION:The airframe comprises a plurality of slave bullets 3 to be shot at a set time, a sensor 3 provided with an offset angle theta to the airframe axis L to sense a target and to measure a distance to the target, and developing wings 5 for applying rotation around the axis L to the sensor 3. The airframe further comprises a computer 6 for calculating a shooting time and number of shooting bullets 2 with the target sensed data obtained from the sensor 3 and data in a data base 7 to set a shooting time to the corresponding bullet 2 and calculating shooting times of the bullets 3 and number of shooting bullets based on the target sensed data of the updated sensor 3 and data in the base 7 to sequentially set shooting times of the residual bullets 2.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a projectile equipped with a plurality of submunitions, and relates to a projectile designed to drop the submunitions above a target area.

[0002]

2. Description of the Related Art Conventionally, as a flying body of this type, for example, there is one shown in FIG.

The flying body 51 shown in FIG. 7 (a) accommodates a plurality of substantially cylindrical cushioning materials 53 holding a plurality of sub-bullets 52 in a case 54 and sets a remote time limit on the head. It has a configuration in which a possible electric timed fuze 55 is attached, and the sub-bullet 52 has a warhead 52a as shown in FIG. 7 (b).
And a ribbon parachute 52b.

When the projectile 51 reaches the sky above the target area, the plurality of sub-bullets 52 are discharged by the operation of the set electric time fuses 55, and the plurality of sub-bullets are discharged. 52 is a ribbon parachute 52b
Will drop in a stable distribution in the target area with a uniform distribution.

The projectile 51 is described in "Latest Defense Technology Taisei", R & D Planning Co., Ltd., February 11, 1985, page 193.

[0006]

However, in the above-mentioned conventional flying body 51, for example, when trying to cover a wide area, a large number of sub-bullets 52 must be mounted, so that the flying body 51 In a situation where the payload is restricted, there is a problem in that it is necessary to miniaturize the sub-bullet 52, and as a result, the power per sub-bullet 52 becomes small.

Further, in this case, since a large number of submunitions 52 are discharged, there is a possibility that the number of unexploded ordnances will increase accordingly. However, it has been a conventional problem to solve these problems.

[0008]

SUMMARY OF THE INVENTION The present invention has been made in view of the problems of the prior art, and even if the power per sub-unit is increased to reduce the number of sub-units to be mounted and the incidence of unexploded ordnance is lowered. ,
It is an object of the present invention to provide a projectile capable of covering most of targets scattered over a wide area and capable of performing a task even for a large target.

[0009]

A projectile according to the present invention comprises a plurality of sub-munitions capable of being ejected at a set time.
Target detecting means provided with an offset angle with respect to the flying machine axis for detecting a target and measuring a distance to the target, and spin imparting means for giving rotation to the target detecting means around the flying machine axis. The target detection data obtained from the target detection means and the data in the database held in advance are used to calculate the shot time and the number of shots of the sub-shot, and the shot time is set and updated for the corresponding sub-shot. In addition, it is configured to include a computer for calculating the shot time and the number of shots of the sub-shots based on the target detection data of the target detection means and the data in the database, and sequentially setting the shot time of the remaining sub-shots. And the structure of such a flying body is a means for solving the above-mentioned conventional problems.

In one embodiment, the wing provided with a cant angle is used as the spin imparting means, and the machine axes of the plurality of sub-units are orthogonal to the projectile machine axis.

An infrared sensor or a millimeter wave sensor can be used as the target detecting means.

[0012]

In the flying object according to the present invention, the rotational force is applied from the spin imparting means to the target detecting means provided with an offset angle with respect to the machine axis.
The instantaneous field of view of the target detection means turns around the machine axis, and when this projectile reaches the sky above the target area and falls, the drop motion of the projectile itself and the swivel motion of the instantaneous field of view of the target detection means. Depending on the combination, the target detection means will perform a spiral search.

Then, when the target is detected by the target detecting means and the target detection data is sent to the computer, the computer determines the time and the number of shots of the sub-shot by the target detection data and the data in the database held in advance. Since it calculates and sets the ejection time for the applicable sub-shot,
These sub-shots will be ejected above the target and will surely drop toward the target.

During this time, when the target detecting means detects a new target, the computer calculates the shot time and the number of shots of the sub-shots based on the updated target detection data and the data in the database. Since the ejection time of the remaining sub-bullets is set sequentially, the sub-bullets set at this time will be ejected toward a new target, and as a result, a single projectile will cover targets scattered over a wide area. It will be.

That is, since the sub-bullets are effectively used one by one, it is not necessary to mount many sub-bullets each having a small power. Therefore, the rate of unexploded ordnance will decrease, and missions for large goals will be fulfilled.

[0016]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

1 to 6 show an embodiment of a flying object according to the present invention.

As shown in FIG. 1, the projectile 1 is in the form of a rocket as a whole, and is used to detect a plurality of sub-munitions 2 and a target (grasp size) and measure a distance to the target. The sensor 3 is provided as a target detecting means to perform.

As shown in FIG. 2, the sub-bullet 2 is formed by mounting an injection motor 2b on a warhead 2a, and the injection motor 2b is ignited at a set time. Each of these sub-bullets 2 is built in side by side in the body of the case 4 such that the machine axis z of the sub-projection 2 and the machine axis L of the projectile 1 are orthogonal to each other.

The sensor 3 is housed in the head of the case 4, and is provided so that the instantaneous visual field S is inclined with respect to the machine axis L by an offset angle θ.

Further, the flying body 1 is provided with a plurality of deploying wings (spin imparting means) 5 at its tail portion. These deploying wings 5 are attached to the case 4 with a cant angle, and the aerodynamic force acting on these deploying wings 5 causes the entire projectile 1 to spin. That is, when the sensor 3 is rotated about the machine axis L, the instantaneous field of view S of the sensor 3 is swung, and as shown in FIG. 3, when the projectile 1 reaches the sky above the target area and falls. In combination with the falling motion of the flying body 1 itself, a spiral search can be performed. And
In this embodiment, the centrifugal force generated by spinning the entire flying body 1 is utilized to promptly separate the plurality of sub-bullets 2 which are stored orthogonally to the machine axis L from the case 4 at the time of ejection. ing.

Further, in this flying object 1, the computer 6 together with the sensor 3 is housed in the head of the case 4. The database 7 of this computer 6 has an offset angle θ of the sensor 3.
And the trajectory data of the submunition 2 are stored, and the graphs of FIGS. 5 and 6 created from the trajectory calculation and the test result at the time of designing the projectile are also stored. In this case, FIG. FIG. 6 is a graph showing the relationship between the distance x to the target at (t ₀ ) and the time Δt from the discovery to the ejection. FIG. 6 shows the size of the target and the distance x to the target and the hit rate SSHP (Single Shot) per sub-shot. Hit Pr
It is a graph which shows the relationship with the availability. Further, in the database 7, the total hit rate P _TH set before the ejection of the sub-shot 2 and the hit rate SSHP per sub-shot are set.
An expression representing the relationship with 1- (1-SSHP) ⁿ > P _TH
Is remembered.

Then, in the computer 6, the ejection time and the number of ejections of the sub-bullet 2 are calculated from the target detection data obtained from the sensor 3 and the data in the database 7, and the ejection time of the sub-bullet 2 is calculated. In addition to setting, the ejection time and the number of shots of the sub-resilience 2 are calculated based on the updated target detection data of the sensor 3 and the data in the database, and the ejection time of the remaining sub-resilience 2 is sequentially set. is there.

Next, the operation of the flying body 1 will be described.

In this flying object 1, the instantaneous field of view S of the sensor 3 turns around the machine axis L because the flying object itself spins by the aerodynamic force generated in the deploying wing 5, so that the flying object 1 is above the target area. When reaching and dropping, the drop motion of the flying object 1 itself and the swivel motion of the instantaneous visual field S of the sensor 3 are combined, and the sensor 3 performs a spiral search in the block 10 of FIG. Become.

Then, when the sensor 3 detects the target in block 11, each data of the size of the target and the distance to the target is sent to the computer 6.

In the computer 6, in block 12, the ejection time (t ₀ + Δt) of the secondary bullet 2 is calculated from the target detection data, the trajectory data from the database 7 and the graph of FIG. Set the total hit rate P _TH of the bullet 2.

Next, in the computer 6, in block 13, the hit rate SSH per sub-shot is calculated from the above-mentioned target detection data and the graph of FIG. 6 sent from the database 7.
P is calculated, and subsequently, in block 13, from the hit rate SSHP per sub-shot and the total hit rate P _TH set previously, the formula 1- (1- of the database 7
SSHP) ⁿ > P _TH , the number n of shots of the sub-bullet 2 is calculated.

Next, when the sub-bullets 2 to be ejected are determined in block 14 and the ejection time (t ₀ + Δt) is set for the corresponding n sub-bullets 2, the sub-bullets 2 are ejected. When the injection time (t ₀ + Δt) is reached, the respective injection motors 2b are operated, whereby the injection motor 2b is injected from the case 4 above the target and surely falls toward the target.

At this time, since the projectile 1 is spinning and the sub-bullet 2 is housed with its machine axis z orthogonal to the machine axis L, the ejected sub-projection 2 interferes with the case 4. Instead, they will be separated quickly.

When the sensor 3 newly detects the target, the computer 6 uses the updated target detection data and the data stored in the database 7 in the same manner as described above.
The injection time and the number of injections of the
Based on the information on the remaining submunitions obtained in
From the remaining sub-bullets 2, decide which sub-bullet 2 to eject,
When the ejection time is set for the corresponding n sub-bullets 2, the sub-bullets 2 set at this time are ejected toward a new target.

That is, since the projectiles 1 alone can cover targets scattered over a wide area, and the sub-bullets 2 are effectively used one by one, it is necessary to mount a large number of sub-bullets with small power per unit. As a result, the rate of unexploded ordnance will decrease and missions for large goals will be carried out with certainty.

The detailed structure of the flying object according to the present invention is not limited to the above embodiment.

[0034]

As described above, according to the flying object of the present invention, since it has the above-described configuration, it is possible to effectively use each sub-bullet to cover most of the targets scattered over a wide area. This makes it possible to increase the power of each sub-munition and reduce the number of sub-munitions to be loaded, thus reducing the rate of unexploded ordnance and in addition fulfilling missions for large targets. It is possible to obtain an extremely excellent effect.

[Brief description of drawings]

FIG. 1 is a sectional explanatory view showing an embodiment of a flying object according to the present invention.

FIG. 2 is an overall perspective explanatory view of a sub-ball mounted on the flying object in FIG.

FIG. 3 is an operation explanatory view showing a target search situation of a flying object in FIG.

FIG. 4 is a block diagram illustrating an operation sequence of the flying object shown in FIG. 1 after discovering a target.

5 is a graph for obtaining the injection time stored in the computer of the flying object in FIG. 1. FIG.

FIG. 6 is a graph for obtaining the number of ejected bullets stored in the computer of the flying object in FIG.

FIG. 7 (a) is an overall perspective explanatory view showing the inside of a conventional flying body in which a sub-balllet is mounted in a broken manner. (B) An enlarged perspective explanatory view of a sub-ball and a cushioning material holding the sub-ball.

[Explanation of symbols]

 1 projectile 2 submunition 3 sensor (target detecting means) 5 deploying wing (spin imparting means) 6 computer 7 database L aircraft axis z projectile axis θ offset angle

Claims (2)

[Claims] 1. A plurality of sub-munitions that can be ejected at a set time, and a target detection that is provided with an offset angle with respect to the axis of the flying machine to detect a target and measure a distance to the target. Means, spin imparting means for imparting rotation around the axis of the flying vehicle to the target detecting means, target detection data obtained from the target detecting means, and data in a database held in advance The number of shots is calculated and the shot time is set for the corresponding bullet, and the shot time and shot number of shots of the bullet are calculated based on the updated target detection data of the target detection means and the data in the database. A flying object characterized by being equipped with a computer for sequentially setting the ejection time of the remaining submunitions by performing the above. 2. The flying object according to claim 1, wherein the wings provided with a cant angle are used as the spin imparting means, and the machine axes of the plurality of sub-units are orthogonal to the projectile machine axis.